基于气压高度辅助的机载自主完好性监测算法

卫星接收机自主完好性监测是指根据用户接收机的多余观测值监测用户定位结果的完好性,其目的是在导航过程中检测出发生故障的卫星,并保障导航定位精度。针对卫星接收机自主完好性监测算法可用性不足的问题,结合机载实际导航系统配置,提出了一种基于气压高度表辅助的机载自主完好性监测算法。综合利用卫星导航系统及气压高度表观测信息,建立联合系统的观测模型,推导了基于多解分离的完好性监测及保护级别计算方法。仿真结果表明,相比于传统的接收机自主完好性监测算法,该算法在可见星为5颗时仍能识别故障卫星。该算法具有更好的故障检测能力及可用性,能有效提高卫星导航系统的完好性监测性能,从而保证卫星导航系统的精度和可靠性。     

卫星通信干扰样式研究

综述通信对抗干扰的分类方式,分析了部分文献中对干扰样式划分的不合理性.根据卫星通信对抗的特点将通信对抗干扰样式进行分类,并从与压制式干扰相区别的角度对欺骗式干扰做出研究分析.     

卫星用两种单相流体回路方案对比研究

单相流体回路系统是航天器主动热控技术中的一种重要方式。文章概述了流体回路的工作原理及理论基础，总结了单相流体回路的设计思路，结合某卫星型号，设计了两种流体回路方案，在SINDA／FLUINT中建立数值仿真模型进行分析计算，并比较了两种方案的应用性能。结果显示，将单相流体回路系统应用于卫星，可取得较好的控温效果。     

根据两颗导航星信息估计捷联惯导系统误差的一种方法

针对高机动短时间飞行的飞行器,介绍了一种根据它相对2颗导航卫星的伪距离和伪速度信息,估计捷联惯导系统定位和定速度误差的方法.考虑到由确定飞行器相对每颗星的径向距离和速度的非线性方程施加的约束,根据这些误差矢量长度最小值的条件确定误差值.用空间解析几何法得出了计算捷联惯导系统误差估值的最终算法,这种算法能给出非线性最小值问题的精确解.     

Development,integrated investigation,laboratory and in-flight testing of Chibis-M microsatellite ADCS

Design, analytical investigation, laboratory and in-flight testing of the attitude determination and control system (ADCS) of a microsatellites are considered. The system consists of three pairs of reaction wheels, three magnetorquers, a set of Sun sensors, a three-axis magnetometer and a control unit. The ADCS is designed for a small 10–50 kg LEO satellite. System development is accomplished in several steps: satellite dynamics preliminary study using asymptotical and numerical techniques, hardware and software design, laboratory testing of each actuator and sensor and the whole ADCS. Laboratory verification is carried out on the specially designed test-bench.In-flight ADCS exploitation results onboard the Russian microsatellite “Chibis-M” are presented. The satellite was developed, designed and manufactured by the Institute of Space Research of RAS. “Chibis-M” was launched by the “Progress-13M” cargo vehicle on January 25, 2012 after undocking from the International Space Station (ISS). This paper assess both the satellite and the ADCS mock-up dynamics. Analytical, numerical and laboratory study results are in good correspondence with in-flight data.     

现代小卫星与大众化空间时代

通过论述现代小卫星技术30年的发展历程,总结其技术发展水平并举出现阶段的典型应用实例,讨论小卫星未来的发展方向,论述大众化空间与现代小卫星的关系,总结现代小卫星技术服务于大众化空间的各项特征。     

航天器的数字化总装设计研究

文章总结了航天器数字化总装设计的基本思路、方法和经验，阐明了数字化总装设计所发挥的作用和意义。     

绳系卫星部署阶段的动力学分析

绳系卫星系统部署阶段末时刻状态决定着其编队飞行的初始状态，为了研究不同因素对绳系卫星系统部署阶段运动的影响，本文建立了一种简单的平面哑铃模型，将系绳视作有阻尼的弹簧，两个卫星视作刚体，考虑重力梯度力矩。通过仿真，发现系绳释放的速度和副星推力是影响绳系卫星系统部署阶段稳定性的主要因素。     

基于拉盖尔函数的卫星姿态预测控制方法

针对卫星在空间站中进行绕飞检测时的姿态控制问题，考虑卫星的姿态轴需要躲避禁飞区域并指向期望位置，提出了一种基于拉盖尔函数的模型预测控制方法，实现了对卫星姿态轴的控制。在模型预测控制方法的基础上，通过拉盖尔函数，将优化多个控制输入转换为优化少数的拉盖尔系数，建立了拉盖尔模型预测的控制策略，改善了传统的模型预测控制方法计算效率差的问题，减少了优化时间。采用卫星在空间站中绕飞的模型进行数值仿真验证，结果表明该方法能够使卫星的姿态轴躲避禁飞区并到达指定位置。与传统方法相比，这种基于拉盖尔函数的模型预测控制策略能够提高优化效率，减少计算时间。     

Zenith Pass Problem of Inter-satellite Linkage Antenna Based on Program Guidance Method

While adopting an elevation-over-azimuth architecture by an inter-satellite linkage antenna of a user satellite, a zenith pass problem always occurs when the antenna is tracing the tracking and data relay satellite （TDRS）. This paper deals with this problem by way of, firstly, introducing movement laws of the inter-satellite linkage to predict the movement of the user satellite antenna followed by analyzing the potential pass moment and the actual one of the zenith pass in detail. A number of specific orbit altitudes for the user satellite that can remove the blindness zone are obtained. Finally, on the base of the predicted results from the movement laws of the inter-satellite linkage, the zenith pass tracing strategies for the user satellite antenna are designed under the program guidance using a trajectory preprocessor. Simulations have confirmed the reasonability and feasibility of the strategies in dealing with the zenith pass problem.